Mounting set, system and method

ABSTRACT

A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.

FIELD OF THE INVENTION

This invention relates to stores carried on dynamic platforms, inparticular rocket propelled missiles and the like carried on air/spacevehicles.

BACKGROUND OF THE INVENTION

There are a variety of different systems for carrying stores on adynamic platform such as an aerospace vehicle, and for deploying thestores therefrom. In one commonly used system, the stores are releasablymounted to mounting stations of aircraft, space vehicles and the like bymeans of lugs integrally formed or permanently fixed on the stores,either externally on pylons, or within a bomb bay or the like, and thelugs may be releasably engaged with release shackles or the like on thecarrier vehicle. The lugs are joined to the stores casing in a mannersuch as to enable it to stand the dynamic loads during operation of thevehicle, and the lugs are provided in the prior art as a unitary itemwith the stores, limiting use of the particular stores with a particularmounting station configuration. However, providing a metal lug joined tothe casing may present difficulties when the casing is non-metallicand/or the casing is thin and/or is subject to significant expansionduring operation of the stores. The latter may be the case, for example,when the stores comprises a rocket engine for propelling a payload,wherein engine experiences expansion during firing.

Examples of some known mounting systems are briefly discussed below.

In U.S. Pat. No. 6,547,182, a solid rocket motor used as a boosterrocket for a launch vehicle is provided with a mounting structure thatincludes a raised hub to which the thrust pin is attached, a series ofaft-directed struts and a pair of transverse struts, all terminating inseparate plates for bolting to the rocket motor case

U.S. Pat. No. 4,736,669 and U.S. Pat. No. 4,829,876 disclose a missilelauncher having an elongate planar platform formed integral with thebody of the launcher. Plural bomb rack fasteners and pylon mounting lugsare fixed to the platform surface to accommodate different aircrafttypes. Plural sway braces are removably fixed to the side edges of theplatform surface. Each sway brace can be fixed to desired positionsalong the side edges of the platform surface to also accommodatedifferent aircraft type mounting apparatus.

U.S. Pat. No. 4,412,475 discloses a jettisonable missile launcher podhas support lugs which extend upwardly through a relatively smallseparate hardback structure to latch into standard release hooks in anaircraft-mounted pylon. The hardback is adjustably attached to the pylonand contains the required high technology electronic gear for themissile system. When the pod is jettisoned, it drops from the releasehooks as usual, but the electronic gear remains with the aircraft in thehardback.

AIAA-2006-1722 (“Mission and System design of Air Launching Rocket UsingMultidisciplinary Optimization Approach”) discloses an air launchedrocket, which is carried on and deployed from the underside of afuselage of a mother aircraft. RS4-2006-2001 (“Responsive Air LaunchUsing F-15 Global Strike Eagle”, 4^(th) Responsive Space Conference2006, Los Angeles) discloses an air launched rocket, which is carried onand deployed from the back of a carrier aircraft. AIAA 2007-6146(“Flight Testing of a Gravity Air Launch Method to Enable ResponsiveSpace Access”, AIAA Space 2007) discloses carrying a rocket in the cargohold of a cargo aircraft, and deploying the same via the aft cargodoors: a drogue parachute is used for facilitating deployment of therocket, after which the rocket may be fired once clear of the aircraft.

SUMMARY OF THE INVENTION

Herein, by “dynamic platform” is meant an artificial structure that inoperation thereof is designed to be subjected to relatively high steadystate accelerations, with respect to up to six degrees of freedom, forexample as induced during transportation and maneuvering in air or inspace. In some cases, such dynamic platforms may experienceaccelerations of up to ±5 g along a longitudinal axis of the platform,and up to ±10 g in directions orthogonal to this axis.

For example, such a dynamic platform may include aerospace vehicles.

Herein by “aerospace vehicle” is meant air vehicles or space vehicles,i.e., vehicles configured for operating in the atmosphere and/or inspace, and capable of powered or unpowered flight therein, and may bemanned or unmanned. Examples of such vehicles may include, inter alia,fixed wing aircraft, rotor wing aircraft, spacecraft, airships,aerostats, satellites, rocket launchers, booster rockets, and so on.Such vehicles are designed to operate in the atmosphere or outsidethereof, when not in direct contact with the ground or sea other than,in some cases, a tether or the like, and thus are configured foroperating in a fluid environment having a density substantially lessthan 1.22 kg/m³, or in a vacuum.

Herein by “pressure vessel” is meant a vessel wherein in operationthereof the vessel may expand as a result of application of internalpressure thereto, the expansion being significant, and may include, forexample, rocket engines and the like.

Herein by “stores” is meant any body that it is desired to mount to thedynamic platform, and may include, inter alia, rockets, missiles, andthe like. In particular, external stores are stores which are designedfor operating, including being mounted, with respect to an outside ofthe dynamic platform, particularly an aerospace vehicle, or stores whichmay be carried mounted to an internal part of the dynamic platform,particularly an aerospace vehicle, but in operation of the stores thestores may be deployed to an outside of the dynamic platform,particularly an aerospace vehicle.

According to one aspect of the invention, a mounting set is provided formounting a stores to a mounting station.

According to this aspect of the invention, a mounting set is providedfor use in mounting an external stores to a mounting station of anaerospace vehicle, comprising at least one strap configured forcircumscribing at least a majority of a perimeter of an external surfaceof said stores in load bearing abutment therewith, and furthercomprising at least one mounting bracket configured for selectivereversible engagement with respect to said mounting station and fortransferring loads between the or each said straps and said mountingstation. The external stores may be externally mounted or internallymounted to the aerospace vehicle.

According to this aspect of the invention, a mounting set is alsoprovided for use in mounting a deployable stores to a mounting stationof an aerospace vehicle, comprising at least one strap configured forcircumscribing at least a majority of a perimeter of an external surfaceof said stores in load bearing abutment therewith, and furthercomprising at least one mounting bracket configured for selectivereversible engagement with respect to said mounting station to enablecorresponding deployment of said stores from said vehicle, and fortransferring loads between the or each said straps and said mountingstation. The mounting set may thus be utilized for externally orinternally mounting a stores with respect to the aerospace vehicle orany other dynamic platform.

By externally mounting is meant that the stores is mounted to anexternal part of the dynamic platform, while by internally mounting ismeant that the stores is mounted to an internal part of the dynamicplatform, the internal part allowing deployment of the stores to anoutside of the platform responsive to disengagement from the mountingstation of the mounting system that includes the mounting set.

According to this aspect of the invention a mounting set is alsoprovided for use in mounting an external stores to a mounting station ofan aerospace vehicle, comprising a mounting bracket arrangement and astrap arrangement, said bracket arrangement configured for selectivereversible engagement with respect to the mounting station and forcooperating with said strap arrangement, said strap arrangement beingconfigured for securing the bracket arrangement to the stores in loadbearing abutment therewith to enable transfer of loads between thestores and said mounting station via said bracket arrangement, inoperation of said mounting set. The said strap arrangement may compriseat least one strap configured for circumscribing at least a portion of aperimeter of an external surface of the stores in abutment therewith.The bracket arrangement my comprise a mounting bracket configured forsaid selective reversible engagement with respect to the mountingstation and a base portion configured for said load bearing abutmentwith the stores.

According to this aspect of the invention, each strap may be configuredfor substantial friction-free abutment with respect to said externalsurface. Commonly, the mounting bracket comprises an attachment lugconfigured for releasable engagement with a complementary hook membercomprised at said mounting station.

The base may be in the form of a saddle member having a contact surfaceconfigured for abutting a part of said external surface, the or eachbracket being joined to said saddle member. The contact surface may beconfigured for substantial frictional abutment with respect to saidexternal surface. In some embodiments, the saddle member comprises atleast one saddle flange for allowing overlying abutting connection ofthe or each said strap with respect therewith such as to sandwich eachsaid saddle flange between said external surface and a correspondingoverlying portion of the or each corresponding said strap duringoperation of said set. The overlying portion of the or each said strapis configured for substantial friction-free abutment with respect to theor each corresponding said saddle flange, and may comprise a coating orlayer of a suitable friction minimizing material.

Each strap may comprise a strip of material having opposite ends, andfurther comprises a suitable connection arrangement configured forconnecting said ends together such as to enable said strap tocircumscribe said perimeter.

Optionally, the saddle member may comprise two axially spaced saidsaddle flanges and having said at least one bracket disposedtherebetween, and further comprising two said straps, each said strapbeing in overlying relationship with a respective one of said saddleflanges.

Optionally, the saddle member may further comprise a primary thrust padconfigured for cooperating with an ejection piston mechanism that may becomprised at the said mounting station during operation of said ejectionpiston mechanism. The primary thrust pad may be in the form of asecondary flange projecting from said saddle flange.

Optionally, the saddle member may further comprise a plurality ofsecondary thrust pads configured for cooperating with a sway bracemechanism that may be comprised at the said mounting station while saidstores is mounted to said mounting station.

According to an aspect of the invention, each strap may be configuredfor elastically deforming to enable accommodation of a variation of saidperimeter within a predetermined range while providing said load bearingabutment with the stores. Each strap may be configured for providingsaid load bearing abutment with the stores for a predetermined range ofexternal loading to said stores via said mounting station, and tofurther allow said elastic deformation while maintaining said loadbearing abutment with the stores. Each strap may be configured forproviding said load bearing abutment with the stores for a predeterminedrange of thermal loading with respect to said stores, and to furtherallow said elastic deformation while maintaining said load bearingabutment with the stores. Each strap may comprise a modulus ofelasticity such as to provide an elastic deformation of at least 0.8%,while providing a datum loading at an elastic deformation of at least0.2%, said datum loading being sufficient to provide said load-bearingabutment at said range of external loads. The external loads may bebetween about 5 g and about 10 g.

When using a metal casing for the stores, the elastic deformation may besubstantially less than 0.5%, for example between about 0.2% and about0.3%, and the baseline tension may optionally be provided at a nominalstrain of about 0.2%, for example.

By way of example the straps may be made from any one of: titaniumalloys, including Ti-β alloys, Ti-15V-3Cr-3Al-3Sn; composite materials,including carbon fiber composites, Kevlar composites; superelasticalloys and/or shape memory alloys including Nitinol, CuZnAl, or CuAlNialloys.

The mounting set may be particularly configured for a stores comprisinga pressure vessel, such as for example a rocket motor.

The said stores may have a substantially circular or oval perimeter, orany other to suitable shape.

According to this aspect of the invention, a mounting system is providedfor mounting an external stores to an aerospace vehicle having at leasttwo mounting stations, comprising for each said mounting station amounting set as defined herein, each said set being mounted to saidstore at a location corresponding to the respective mounting station.Each said mounting station may comprise a release shackle arrangementfor releasably engaging said bracket. In some embodiments, the mountingsystem comprises two said mounting sets, each said set comprising a pairof said straps axially displaced from one another.

An aerospace vehicle is also provided comprising at least one storesmounted thereto using a mounting system as defined herein. For example,such a vehicle may be a UAV. Optionally, at least one said stores is anexternal stores mounted to a wing or underbelly of said vehicle.

A method is also provided for mounting a stores to an aerospace vehiclemounting station, comprising:

providing a mounting system as defined herein;

engaging each said set with respect to said stores; and

engaging each said mounting bracket to a respective said mountingstation of said vehicle.

In step (b) said sets may be axially spaced from one another along adirection substantially orthogonal to said perimeter by a spacingsubstantially corresponding to a spacing between said mounting stations.Further in step (b), said straps may be in abutting load bearing contactwherein a baseline tension is provided on said straps, said baselinetension being sufficient for ensuring that said straps remain inabutting load bearing contact with said stores for a full range ofoperating conditions for said stores. Said baseline tension may be suchas to enable the straps to be elongated elastically sufficiently toaccommodate preset changes in ambient temperature and/or preset changesin said perimeter of said stores during operation thereof.

The method may further comprise the step (d) of selectively disengagingeach said mounting bracket from its respective said mounting station toenable release of said stores.

Optionally, the stores may comprise a rocket motor, and the methodfurther comprises the step of igniting said motor.

Optionally, the method may be applied to retrofitting a stores with atleast one said mounting set for enabling the stores to be mounted to anydesired aerospace vehicle, the or each mounting set being configured forengagement to a respective mounting station of said aerospace vehicle.Optionally stores does not previously comprise an integral mountingsystem for mounting the stores to an aerospace vehicle. Alternatively,the stores comprises an integral mounting system for mounting the storesto the aerospace vehicle or to another type of aerospace vehicle.

According to embodiments of the invention, a mounting system is providedcomprising at least one mounting set for use in selectively mounting anddeploying a stores with respect to a mounting station of an aerospacevehicle, the or each mounting set comprising a mounting bracketarrangement and a strap arrangement, said bracket arrangement configuredfor selective reversible engagement with respect to the mounting stationand for cooperating with said strap arrangement, said strap arrangementbeing configured for securing the bracket arrangement to the stores inload bearing abutment therewith to enable transfer of loads between thestores and the mounting station via said bracket arrangement when saidbracket arrangement is engaged with the mounting station, said bracketarrangement being selectively disengageable from the mounting station toenable corresponding deployment of said stores from said vehicle.

According to another aspect of the invention, a mounting set is providedfor use in mounting a pressure vessel to a dynamic platform, thepressure vessel comprising a surface having a perimeter that is variablewithin a range during operation of said pressure vessel, the mountingset comprising at least one strap configured for circumscribing at leasta majority of said external surface in a direction substantiallyparallel to said perimeter and in load bearing abutment with saidexternal surface, and further comprising at least one mounting bracketconfigured for reversible engagement with respect to said dynamicplatform and for transferring loads between the or said straps and saiddynamic platform, the or each said straps being configured for providingsupport to said pressure vessel with respect to said dynamic platformwhile accommodating said variation of said perimeter within said range.The stores may be adapted for being deployed from the platform duringoperation of the stores.

The or each said at least one mounting bracket may be configured forreversible engagement with respect to a single mounting point comprisedin said dynamic platform and for transferring loads between the or saidstraps and said mounting point.

A method is also provided for mounting a pressure vessel to dynamicplatform, comprising:

-   -   (a) providing a plurality of mounting sets as defined herein;    -   (b) engaging each said set with respect to said external        surface; and    -   (c) engaging each said mounting bracket to a respective mounting        station of said dynamic platform.

Thus, according to at least some embodiments of the invention a mountingstructure is provided that permits attachment of a rocket motor (orother expandable pressure vessel, mutatis mutandis) to a dynamicplatform such as an aerospace vehicle, in a manner that accommodates theexpansion of the rocket motor that occurs during operation thereof,and/or withstands the stresses associated with operating such a dynamicplatform at aggressive g-loads in any direction, in a relatively simpleand cost effective manner, and in a manner that may optionally beapplied for retrofitting existing stores designs, whether the existingstore design does not include any mounting arrangement, or whether theexisting stores design already includes a mounting arrangement. Thus,the invention may be applied to a wide range of hardware that has nospecial provision for mounting to an aerospace vehicle or other suitabledynamic platform, and may be modified in a simple and cost effectivemanner to enable the same to be transported on the aerospace vehicle ordynamic platform in a similar manner to a standard external stores bymatching the one or more mounting sets to the particular size, weight,expansion characteristics and so on of the hardware on the one hand, andthe position of the mounting stations onto which it is to be mounted, onthe other hand. The mounting sets do not normally require anymodification of the hardware, except for example providing suitablerounded edges for applications where the straps of the mounting setswould otherwise need to be abutted over sharp edges, and thus themounting sets may be removed from the hardware after use, asappropriate, without causing damage.

Referring to existing stores that already have integral mountingarrangements, it is to be noted that such arrangements are specific toone type of mounting station configuration. According to aspects of theinvention, one or more mounting sets may be fastened to such stores toenable the stores to be used with any other mounting stationconfiguration, part or all of the integral mounting arrangement thenbecoming redundant. In some cases it may be useful to simply add amounting set according to embodiments of the invention to assist insupporting or in distributing load of such an existing stores.

The invention also provides a relatively simple and cost effectivesystem and method of mounting a new stores which may be constructed fromexisting components of other stores, but where the weight and/or centerof gravity may be different therefrom, allowing the mounting sets to bedistributed in an appropriate manner with respect to the new stores tomatch the carrier vehicle arrangements

According to an aspect of the invention, an attachment device for arocket motor is provided, the attachment device comprising a saddlefastened with straps, the saddle comprising an interface for enablingattachment to a dynamic platform.

Some features of at least some embodiments of the invention include thefollowing:—

-   -   In normal operation, the stores may be disengaged from the        dynamic platform without causing damage to the saddles or to the        casing of the stores.    -   Disengagement of a rocket-propelled type stores from the dynamic        platform may be performed in steady flight conditions or even in        extreme dynamic maneuvers, whether the rocket motor is fired        prior to or after disengagement.    -   In some embodiments comprising rocket propelled stores, these        stores may be configured for being attached to the dynamic        platform for most or all of the duration of firing of the rocket        motor—for example for use in rocket assisted take-off for        aircraft, or for use as auxiliary rockets for missiles etc.    -   The saddle member(s) may be attached to the external surface of        the stores, such as a motor casing, for example, via the straps        without any need for prior preparation of the stores, when the        casing is a pressure vessel or otherwise does not include        relatively sharp corners over which the straps are to abut.    -   The relative location of each mounting set, in particular the        mounting bracket, i.e., the number of mounting sets and relative        distance inbetween sets may be determined according to the        interface requirements of the dynamic platform.    -   The mounting sets, in particular the mounting brackets may be        positioned with respect to the stores such as to minimize        dynamic load, such that the center of gravity of the stores is        at the geometric center of suspension when two or more        substantially similar mounting sets are used. When a single        mounting set is used, this may be located aligned with the        centre of gravity of the stores. Alternatively, when a number of        mounting sets are used, each rated for taking a different        proportion of the dynamic load associated with the stores, a        weighted center of suspension may be calculated according to the        distribution of dynamic load, and this weighted center of        suspension and this may be located aligned with the centre of        gravity of the stores.    -   A modular mounting system is provided, in which each mounting        set acts as a module that may be used with any number of        different vehicles, and with any number of different types of        stores.    -   The mounting set allows the same stores, for example a        particular rocket or missile, to be mounted to a variety of        different dynamic platforms, for example different types of        aircraft pylons, without requiring any particular modification        to the stores itself: rather the relative locations of the        mounting sets with respect to the stores may need to be changed        for matching the pylon configuration of the different platforms.    -   No additional mounting elements are required for mounting the        stores to the dynamic platform, and loads between the stores and        the dynamic platform are transmitted via a relative large        contact area between the straps and casing surface.    -   Using straps with high elasticity, low weight or density, and        high tensile strength can enable the casing loading for the        stores to be minimized    -   The number of saddle member may be secured to the motor (each        using one or a plurality of straps) may be determined according        to the number and relative spacing of the mounting stations,        i.e. the nature of the platform interface—there is also the        flexibility of using in some cases less mounting sets than there        are number of mounting stations, depending on the size of the        stores, weight, and so on, for example;    -   It may be possible at least for some embodiments to control the        level of fastening of the saddle member to the stores, and thus        to match any intensity of the dynamic maneuver (within limits)        that it is desired to subject the stores to, by varying the        friction between the saddle member and the casing, and the        baseline tension applied to the straps.    -   Suitable materials for the straps may be chosen to provide        relatively high elasticity and tensile strength coupled with        relatively low thermal expansion coefficient.    -   The straps may be configured as relatively thin flat strips,        thereby minimizing drag when mounted to an aircraft, or when        deployed therefrom.    -   The mounting sets, in particular the saddle member, may be        configured for receiving a mechanical impulse from a pyrotechnic        piston arrangement or the like, used for facilitating separation        of the stores from an aircraft body in flight, thereby        preventing possible damage to the stores casing and/or allowing        a relatively stronger impulse to be provided.    -   The mounting sets, in particular the saddle member, may be        configured for cooperating with sway braces, and different        geometries of saddle members may be provided for cooperating        with different sway brace geometries, for any particular stores.    -   The mounting sets are not generally sensitive to manufacturing        tolerances, including diameter uniformity of the stores, and        thus can lead in some cases to manufacturing cost reductions,        where the stores may be manufactured to less stringent        tolerances.    -   The mounting sets may also be used for mounting a stores        internally in a dynamic platform. For example, in aircraft that        are configured for accommodating stores such as missiles, bombs        etc. in bomb bays or the like can have these stores mounted        therein using the mounting sets.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to understand the invention and to see how it may be carriedout in practice, embodiments will now be described, by way ofnon-limiting example only, with reference to the accompanying drawings,in which:

FIG. 1 is side view of a mounting system including mounting setsaccording to a first embodiment of the invention, used for mounting astores to a vehicle.

FIG. 2 is a top rear isometric view of the mounting system embodiment ofFIG. 1 fastened to a stores.

FIG. 3 is a detail of a marked part of FIG. 2. FIG. 3( a) illustrates avariation of the embodiment illustrated in FIG. 3.

FIG. 4 is a partial cross-sectional top rear isometric view of theembodiment of FIG. 1, the cross-section taken along X-X in FIG. 1.

FIG. 5 illustrates in partial cross-sectional view an example of aconnection arrangement of the embodiment of FIG. 1; FIG. 5( a)illustrates the embodiment of FIG. 5 along the direction of arrow A.

FIG. 6 schematically illustrates an example stress-strain graph for amaterial for the straps of the embodiment of FIG. 1.

FIG. 7 illustrates in top isometric view a variation of the mounting setembodiment of FIG. 1.

FIG. 8 illustrates in top isometric view another variation of themounting set embodiment of FIG. 1; FIG. 8( a) illustrates incross-sectional view a detail marked in FIG. 8.

FIG. 9 illustrates in top isometric view a mounting set according to asecond embodiment of the invention.

DETAILED DESCRIPTION OF EMBODIMENTS

Referring to FIGS. 1 to 4, a mounting system according to a firstembodiment of the invention, generally designated 100, is provided forselectively and releasably engaging a stores 150 with respect to adynamic platform 170.

In the first embodiment, and referring particularly to FIG. 1, thedynamic platform 170 comprises a carrier vehicle, in particular anaerospace vehicle, such as for example an aircraft, which may be amanned aircraft of an unmanned air vehicle (UAV), for example, thoughthe invention may be applied, mutatis mutandis, to any other suitabledynamic platform. In this embodiment, the stores 150 may be mounted withrespect to a standard mounting structure, or indeed to any othersuitable mounting structure, provided in the dynamic platform. By way ofexample, the mounting structure is that of a standard wing pylon 175,comprising a pair of axially spaced mounting stations 176 a, 176 b, eachstation comprising a release shackle 177 having a hook 178 thatcooperates to selectively engage/disengage with a hanger lug that isdesigned to be provided with an external store that it is desired to bemounted to the mounting station, enabling selective deployment of thestores with respect to the vehicle. Each mounting station commonlyincludes a pair of swing braces (not shown) in laterally spacedrelationship with respect to the release shackle 177, for providingstability to the stores. Optionally, a release pyrotechnic piston (notshown) may also be provided for mechanically generating a separationimpulse to the stores when this is released from the pylon to aid indistancing the stores therefrom. For example, common standard suchmounting structures provide a pair of such hooks 178 axially separatedfrom one another by a spacing of 14 inches for light stores, or by aspacing of 30 inches for heavy stores. However, the invention may beapplied, mutatis mutandis, to any other suitable mounting structure.

By way of example, the stores 150 comprises a missile, rocket or thelike, having an aft solid rocket engine 155, comprising a substantiallycylindrical casing 156 defining a pressure vessel, accommodating a solidfuel propellant, and a nozzle 159 at the aft end. Alternatively, thestores may comprise a rocket engine using gaseous or liquid propellant.The casing 156 has an external surface 159, and a perimeter P taken in adirection substantially orthogonal to the longitudinal axis 99 of thestores 150. A payload 151, comprising for example explosives and/orguidance/targeting/surveillance systems, may be provided at the fore endof the stores 150. When the rocket engine 155 is fired, commonly but notexclusively after release and separation from the carrier aircraft, thecasing 156 expands due to the thermal and pressure buildup in thecombustion chamber of the rocket engine 155. Where the carrier vehicleis an aerospace vehicle, where there are weight considerations, casing156 may in some embodiments comprise a relatively thin thickness,commonly of the order of 0.05 cm to about 2.5 cm, and such casings 156may commonly expand in diameter between about 0.1% to about 0.6% formetallic casings, or between about 0.3% to about 1.8% for compositecasings, depending on the particular configuration of the stores. Whilecasing 156 is commonly tubular/cylindrical, having a circular perimeter,other embodiments of the invention are also applicable, mutatismutandis, to other types of casings, for example frusto-conical orconical casings, casings having different diameters at different axiallocations; casings having an oval or polygonal cross-section andperimeter, including a generally triangular or rectangular cross-sectionand perimeter.

Referring in particular to FIG. 2, the mounting system 100 comprises apair of mounting sets, 10 a and 10 b respectively fastened to a fore andaft location of the stores 150. The particular locations of the mountingsets 10 a, 10 b are such as to be in registry with the stations 176 a,176 b of the carrier vehicle when the stores 150 is mounted thereto. Themounting sets 10 a and 10 b in this embodiment are substantiallyidentical structurally, and will be referred to collectively by thenumeral 10, and are located along the casing 156 on opposite axial sidesof the centre of gravity CG of the stores 150 for providing a staticallybalanced configuration when the stores 150 is mounted to the carriervehicle 170. Accordingly, it is possible for at least one of themounting sets to be fastened to a different part of the stores 150 awayfrom the casing 156.

Each said mounting set 10 comprises an attachment or mounting bracket 13in the form of a lug configured for cooperating with hook 178 of therespective mounting station. The particular geometry of the bracket 13is generally complementary to, and corresponds to, the particular hookgeometry onto which it is wished to mount the stores 150 via themounting system 100. It is to be noted that in applications of theinvention in which the mounting stations comprise a differentconfiguration for engaging with stores, the bracket 13 follows theconfiguration required for enabling engagement with the mountingstation.

The bracket 13 is rigidly joined to a base in the form of a generallyrigid saddle member 12, either integrally or in any suitable manner, forexample welding, bolting and so on, and the bracket 13 projectsoutwardly from the outer convex side of the saddle member 12. The saddlemember 12 acts as a load being interface between the bracket 13 and thestores 150. Referring also to FIG. 4, the saddle member 12 comprises asubstantially concave surface 21 that is generally complementary to theexternal surface 159 of the store onto which the saddle member 13 is tobe fastened. The thickness and material of the saddle member 12 andbracket 13 are such as to enable loads to be transmitted directly orindirectly between the stores 150 and the mounting stations, whilemaintaining mechanical integrity of the saddle member 12 and bracket 13.Optionally, a friction inducing coating or layer 17 is provided on saidsurface 21, for example a thin elastomeric or rubber layer, or the like,optionally glued (or otherwise affixed) to the surface 21. The saddlemember 12 comprises a pair of flanges 23 a, 23 b axially extending inopposite directions from a central portion 24 of the saddle member 12onto which the bracket 13 is joined.

The saddle member 12 is fastened onto the casing 156 by means of a pairof substantially identical tension straps 14. Each strap 14 comprises astrip 37 of material having a width w, thickness t and length l, andenlarged ends 36, and is configured for being looped around at least amajority of or the full perimeter P, partly in direct load-bearingcontact with external surface 159, and partly in indirect contactthereto by being in abutting load bearing contact with a correspondingflange 23 a or 23 b. Thus, a portion 34 of each strap 14 is in overlyingand abutting relationship with a corresponding flange 23 a or 23 b, andin this embodiment the portion 34 comprises the enlarged ends 36including a suitable connection arrangement 40 to connect the said ends36 together such as to enable the strap 14 to circumscribe the perimeterP and maintain a looped configuration with respect thereto. In thisembodiment, the connection arrangement is also configured to provide thecorresponding strap 14 with a baseline tension T₀ for maintaining thesaddle securely fastened to the casing 156 for a range of conditions,and thus prevent the strap 14 from loosening over the casing 156, aswill be described further herein. The length l is generally determinedby the perimeter P of the stores 150, taking into account the effectivecircumferential length of the connection arrangement 40.

Thus, the mounting set 10 enables the bracket 13 to be fastened to thestores in a bolt-free, rivet free, or weld-free manner with respect tothe casing 156, enabling the location of the bracket with respect to thestores to be varied during the fastening operation, and further enablingthe mounting set to be removed from the stores without damaging thesame.

Optionally, and as illustrated in FIG. 3( a), one or more loops orcarriers 19 may be provided, integrally formed or joined to the saddlemember 12, for slidingly holding at least one end of each belt 14 inplace with respect to the saddle member 12, and thus facilitatingassembly of the mounting set 10 with respect to the stores 150.

The connection arrangement 40 comprises a plurality of tension bolts 42,rivets or the like, that engage the enlarged ends 36 via a correspondingplurality of apertures 43 formed in each end 36. Alternatively, suitablemechanical clamps may be provided for connecting the enlarged ends 36.In the illustrated example, the bolts 42 may be turned until the torquecorresponds to baseline tension T₀. Alternatively, when rivets are usedinstead of bolts 42, the length of the rivet may be chosen such as toprovide a spacing S between the ends 36 when engaging the two together,this spacing S being such as to provide the baseline tension T₀.

Alternatively, and referring to FIG. 5 and FIG. 5( a), an alternativeconnection arrangement 40′ is illustrated, comprising, instead of boltsor rivets, a pin arrangement 41 having a central shaft 44 with heads 45for abutting against complementary shoulders 46 formed in said apertures43. The in-situ length S₁ of the shaft 44 is such that when the pin 41is in place with the heads 45 in abutment with the shoulders 46, thisinduces baseline tension T₀ in the corresponding strap 14. To facilitateengagement of the heads 45 with the corresponding shoulders 46, throughslots 48 having a width at least a little larger than the diameter ofthe shaft 44, are provided from an upper edge 49 (as seen in FIGS. 5 and5( a)) to the corresponding aperture 43 to allow the shaft 44 to passtherethrough and settle on the corresponding aligned pair apertures 43of the facing ends 36.

In one variation of the embodiment of FIGS. 5 and 5( a), the pin 41 isengaged with the ends 36 by forcing the ends 36 together closer togetherthan is required to fit the shaft 44 therebetween, providing a distancebetween the shoulders 46 less than S₁, thereby permitting enoughclearance for inserting the pin through the slots 48 and into positionwith respect to apertures 43. When the ends 36 are released, the heads45 engage the shoulders 46 and provide the baseline tension T₀.

In another variation of the embodiment of FIGS. 5 and 5( a), theconnection arrangement comprises a thermal connector, and pin 41 is madefrom a so-called shape memory alloy (SMA), for example Nitinol (Ti 50%,Ni 50%), CuZnAl, or CuAlNi alloys. The SMA is chosen to have anAustenite finish (Af) temperature less than the lowest operatingtemperature Temp_(min) of the stores 150. To fit the pin 41 intoposition with respect to the ends 36, the pin 41 is cooled to atemperature well below the Austenite start (As) temperature, or belowthis to the Martensite start (Ms) temperature, allowing the pin to bedeformed (indicated at 41′ in FIG. 5) to a longer shaft length S₂,sufficient for the heads 45 to clear the shoulders 46 when the strap 14is in a non-stressed state. With the deformed pin in place, the pin isheated to the Af temperature, and assumes its original length S₁,bringing together the ends 36, and providing the baseline tension T₀ tothe strap 14.

Alternatively, the straps may each be formed as a closed loop (notillustrated) made from a shape memory alloy (SMA), for example Nitinol(Ti 50%, Ni 50%), CuZnAl, or CuAlNi alloys. The SMA for the strap ischosen to have an Austenite finish (Af) temperature less than the lowestoperating temperature Temp_(min) of the stores 150. To fit the strapinto position with respect to the casing 150, the strap is cooled to atemperature well below the Austenite start (As) temperature, or belowthis to the Martensite start (Ms) temperature, allowing the strap to bedeformed to a larger diameter, sufficient for the strap to be broughtinto position overlying the saddle flanges and the casing. With thestrap in place, the strap is heated to the Af temperature, and assumesits original diameter, contracting over the saddle and casing such as toprovide the baseline tension T₀ to the strap.

The inner-facing surface 51 of each strap 14 may be coated or comprise alayer of frictionless or lubricating material, for example based on orcomprising Teflon or molybdenum disulphide, such as to minimize orprevent friction or shear forces being induced between the strap 14 andthe external surface 159 and/or the corresponding flange 23 a or 23 bwhen in load bearing abutment therewith. Thus, in said load bearingabutment, loads can be transmitted between the mounting stations and thestores 150 via the bracket 13, saddle member 12, and optionally thestraps 14, without adding unnecessary additional stress to the straps 14which may otherwise be generated if substantial friction and/or shear ispresent between the straps 14 and the surface 159 and/or thecorresponding flange 23 a or 23 b. Such additional stress would requirethe cross-section of the straps 14 to be greater, and/or for the strapmaterial to have a different modulus of elasticity. According to anaspect of the invention, loads components along 99 are not substantiallyresisted by the straps, but rather primarily via frictional contactbetween the saddle member and the casing, while radial load componentsmay in addition also be resisted by the straps.

Thus, during operation of the stores 150, while mounted to the vehicle170 such as an aircraft or other aerospace vehicle, the stores 150 maybe subjected to dynamic loads during lift-off as well as duringmaneuvering. After disconnecting and deploying the stores from thevehicle 170, by disengaging the hooks 178 from the brackets 13, themounting sets 10 remain fastened on the casing 156. After disconnectionand deployment of the stores, and in some case prior thereto, the rocketmotor 159 is fired, and the casing is pressurized to a high pressure,and according to an aspect of the invention during operation of themotor 159, or at least while the pressure in the casing 156 is aboveambient, the straps 14 deform generally following the elastic strain ofthe casing 156 in order to prevent stress concentration on the casing156 by the straps 14. The expansion may vary and at least partiallyreverse during operation of the motor.

Thus, in this embodiment, the straps 14 are further configured foraccommodating the range of expansion of casing 156 undergoes duringoperation of the rocket motor 159, on the one hand without inducingbuckling or bursting stresses on the casing 156, while on the other handmaintaining the saddle member 12 firmly fastened onto the casing 156 forthe full range of loading induced by dynamic maneuvers carried out bythe carrier vehicle. Such maneuvers may include accelerations anddecelerations along any of three orthogonal axes of the aircraft, and/orrotational movements about said axes, pitch roll and yaw. The straps 14may thus be made from a suitable material having such properties.Referring to FIG. 6, an example stress-strain graph is illustratedshowing some of the properties that may be required of the material fromwhich the straps 14 are made. Line OB represents elastic deformation ofthe strap 14, while line BC represents plastic deformation. The materialis capable of providing a baseline elastic strain ε₀ corresponding tothe baseline tension T₀ (for a given strap cross-sectional area) that issufficient for maintaining the mounting set 10 securely fastened ontothe casing 156, for the full range of dynamic loads transferred from thecarrier vehicle thereto via the brackets 13. The greater the levels ofdynamic load expected to be experienced by the set 100, the larger T₀needs to be. It is also to be noted that the larger the sum of thecross-sectional areas of the straps 14 for a given material, the lowerthat ε₀ needs to be to support a given dynamic load, since the samebaseline tension may be provided at a lower stress level. A common valuefor ε₀ may be about 0.3%, but the actual design value for any particularstores may depend on the range of operating temperature, expansioncharacteristics of the belts and/or of the casing, among other factors.At the same time, there is a potential strain increment Δε wherein thestrap 14 may deform elastically. According to an aspect of theinvention, a material for the straps 14 may be chosen such as to providea potential strain increment Δε that is matched to the expectedexpansion of the casing 156 during operation of the rocket motor 159:for example, if the expected casing expansion is about 0.5%, thematerial needs to have a potential strain increment Δε over and abovethe baseline strain ε₀ that is needed to provide the baseline tension T₀in the straps, which, if for the sake of example is 0.3% results in arequirement for an elastic strain ε_(r), and thus an elastic strainlimit ε_(B) of not less than 0.8%. The value of potential strainincrement Δε generally depends on the thickness and material of thecasing, the rating of the rocket motor, among other factors.

Furthermore, the baseline elastic strain ε₀ represents the baselinetension T₀ at a nominal operating ambient temperature, say 0° C.According to this aspect of the invention, given an operatingtemperature expected to be experienced by the straps 14 between aminimum temperature Temp_(min) and a maximum temperature Temp_(max), sayfor example between about −50° C. and about +120° C. (, respectively thematerial of the straps is still capable of providing the requiredperformance therefor. For example, the corresponding reduction in thebaseline tension to T_(0min) at Temp_(max) as a result of the thermalexpansion of the belt 14 relative to the casing 156, which may notexpand significantly if made from a composite material and/or has arelatively higher thermal mass than the straps, is still sufficient formaintaining the mounting set 10 securely fastened onto the casing 156,for the full range of dynamic loads transferred from the carrier vehiclethereto via the brackets 13. At the same time, the higher strain ε₂ thatresults at Temp_(min) due to thermal contraction of the belt 14, whenadded to the potential strain increment Δε for accommodating theexpansion of the casing 156, effectively pushes the requirement for anelastic strain ε_(r) further towards, but not exceeding the elasticstrain limit of ε_(B). Thus, if by way of example ε₂ is about 0.35%,ε_(r) needs to be 0.85, and thus the elastic limit needs to be not lessthan 0.85%.

Suitable materials for the straps provide a good combination of goodtensile strength and low elastic modulus, and preferably also lowthermal expansion coefficient. Such materials may include, by way ofexample, metal alloys, such as for example, titanium alloys in general,including titanium beta alloys (Ti-β), such as for exampleTi-15V-3Cr-3Al-3Sn at an ‘annealed’ state. The Titanium alloyTi-15V-3Cr-3Al-3Sn has a low modulus of elasticity (E=7900 Kg/mm²) and ahigh tension strength, therefore the elastic strain reaches about 1%,for example capable of matching the strain of a casing 156 made fromcarbon fiber or the like.

Other suitable materials for the straps 14 may include Nickel-Titaniumalloys (NITINOL) or other metals that are superelastic and/or have shapememory characteristics, or epoxy carbon or Kevlar fibers, and so on.

The extent of fastening required, i.e. the required baseline tension T₀,may be determined according to the dynamic forces which the stores 150is to be subjected to, herein referred to as design dynamic forces. Byway of non-limiting example, a stores 150 having a weight of 1000 Kg anddesign dynamic forces of 10 g acting thereon parallel to the axis 99,and attached to the dynamic platform 170 via two mounting sets, and thustwo brackets 13, the force acting on each bracket is 0.5×(10×1000Kg)=5,000 Kg.

Assuming the mounting set configuration of FIGS. 1 to 4, each bracket 13being fastened to the stores 150 by two straps 14 of cross section A(=width w*thickness t), and the friction coefficient between the saddlemember 12 and the casing 156 is μ=0.5, which may be achieved byproviding, for example, one or more rubber sheets for layer 17, aminimal tension T in each strap 14 is determined as:

${T = {{( \frac{5000\mspace{20mu} {Kg}}{\mu = 0.5} ) \cdot \frac{1}{4}} = {2500\mspace{20mu} {Kg}}}}\mspace{14mu}$

It may be required that this minimal fastening exists for a strain ε of0.25% (the value of which generally depending on the modulus ofelasticity and the combined cross sectional area of the straps) in thestrap, this when the temperature of the strap and casing are atTemp_(max), noting that a metal strap expands due to heating generallymore than a casing made from composite material.

The nominal cross-sectional area A required for the strap 14 may beobtained from the baseline tension T₀ and strain ε₀ for a given materialhaving a modulus of elasticity E:

T ₀ =E*ε ₀ *A

Thus, for the above example where T₀=2,500 Kg, ε₀=0.3% and assuming thestraps are made from a Ti-β alloy having E=7900 Kg/mm², thecross-sectional area for each strap 14 is 105 mm². Any suitablecombination of strap width w and thickness t may be used to provide therequired cross-sectional area, for example: thickness 1 mm, width 105mm; thickness 1.5 mm, width 75 mm. In particular, while the thickness tis generally maintained as thin as possible to reduce drag, the width wmay be chosen sufficiently large such that the surface pressure providedby the strap 14 on the casing 156, by means of its contact areatherewith (length l*width w) is within the allowable limit to preventthe casing buckling or bursting, particularly when subjected to theexpanding forces generated by the rocket motor 159. At the same time,very thin straps may be problematic in maintaining mechanical integrity.Thus, it is appreciated that the straps distribute the stresses over acircumference of the casing. Similarly, the contact surface 21 of thesaddle member 12 may be made as large as possible to spread the forcetransmitted via the corresponding bracket 13 over as large an area aspossible of the casing 156, to minimise the possibility of buckling orbursting of the casing 156, while avoiding providing straps that are toothin.

Optionally, and as illustrated in FIG. 3, the saddle member 12 maycomprise a primary thrust pad 62 configured for cooperating with theejection or pyrotechnic piston mechanism that may be comprised at thecorresponding mounting station during operation of said pistonmechanism. Thus, the relative position of the primary thrust pad 62 withrespect to the bracket 13 corresponds to the relative position of thecorresponding piston mechanism with respect to the corresponding hook178.

Further optionally, the saddle member 12 may also comprise secondarythrust pads 64 configured for cooperating with a sway brace mechanismthat may be comprised at the corresponding mounting station while saidstores is mounted to said mounting station. Thus, the relative positionsof the secondary thrust pads 64 with respect to the bracket 13correspond to the relative positions of the corresponding sway braceswith respect to the corresponding hook 178.

Alternatively, the saddle member 12 may be formed with a larger flange23 a that extends axially and optionally circumferentially sufficientlyto provide cooperation with the aforesaid piston and sway braces.

While the mounting system 100 according to the first embodiment has beendescribed comprising two mounting sets 10, each having two straps 14, itis to be appreciated that the mounting system may comprise more than twomounting sets, or indeed only one mounting set, generally depending onthe mounting configuration available at the dynamic platform, and on thesize and weight of the stores 150. Furthermore, each mounting set 10 maycomprise more than two straps each, mutatis mutandis.

Alternatively, an in a variation of the first embodiment, each mountingset may comprise a single strap, but is otherwise similar to the firstembodiment, mutatis mutandis. For example, as illustrated in FIG. 7, thefree ends 36′ of the illustrated single strap 14′ are axially wider thanthe bracket 13, and are connected to one another by means of bolts,rivets, pins and so on, as described above, mutatis mutandis, butaxially displaced from the bracket 13 or in any other manner that doesnot interfere with the bracket 13 nor with operation of the hook 178.Alternatively, and referring to FIG. 8, in the single strapconfiguration illustrated, the strap 14″ includes two strap arms 14 a,14 b extending in opposed directions from a strap ring 14 c whichincludes an opening 14 d to allow the bracket 13 to extend therethroughwhen the ring 14 c, and possibly parts of the strap arms 14 a, 14 b, arein generally frictionless but load bearing contact with saddle member12. The opening 14 d may be made sufficiently large to allow forrelative transverse movement between the ring 14 c and the saddle member12 when the bracket 13 is accommodated in the opening 14 d. In theembodiment of FIG. 8, the ends 36 of the strap arms 14 a, 14 b areconnected in substantially the same manner as described earlier, mutatismutandis, with the difference that rather than this connection beingmade in overlying relationship with the saddle member 12, as is the casethere, the connection is made directly over the casing 156 at adifferent circumferential position with respect thereto, for example ata position diametrically opposed to the position of the bracket 13.Optionally, and as illustrated in FIG. 8( a), a stiffening member 66 maybe provided that is engaged between the enlarged ends 36 a, 36 b of thestrap arms 14 a, 14 b. The stiffening member 66 may be in the form of ametallic tab, rod or the like, for example, that projects from end 36 band is received in a tight fit within a complementary recess in theopposite end 36 a, and is configured for minimizing or preventing theends 36 a, 36 b from deforming in an outward radial direction when themounting set is subjected to high stress. Optionally, a load transferpad 61 may be provided, sandwiched between the ends 36 a, 36 b and thecasing 156, the surface of the pad facing the casing being preferably infrictional, load-bearing engagement with the casing.

Furthermore, it is also to be noted that in other embodiments of theinvention, different types/configurations of mounting sets may beemployed for use with a particular stores. For example where it isdesired to support a stores at the center of gravity, a mounting setdesigned to carry most of the weight and dynamic stresses of the storesis fastened on the stores at its center of gravity, and one or twolighter duty mounting sets may be provided axially spaced therefrom toprovide longitudinal stability. Alternatively, the stores may comprise across-section or diameter that varies along its longitudinal length, anddifferent mounting sets with different-length straps may be provided atdesired locations.

A second embodiment of the invention, illustrated in FIG. 9, comprisesall the features and elements of the first embodiment and variationsthereof, mutatis mutandis, and thus the mounting set 200 according tothis embodiment comprises a bracket 213, saddle member 212, and a pairof straps 214 substantially similar to the bracket, saddle member andstraps of the first embodiment, mutatis mutandis. However, in the secondembodiment, the straps 214 are not in frictionless overlyingrelationship with the saddle member 212. Rather, the straps 214 arejoined to the saddle member 212, so that the enlarged ends 236 of thestraps are joined to one another by the connecting arrangement 40 at adifferent location. For example, and as illustrated in FIG. 9, thestraps 214 each comprise a pair of strap arms 214 a, 214 b extendingfrom the sides 267 of the saddle member 212, and the enlarged ends 236of the strap arms 214 a, 214 b are connected using the connectionarrangement 40, and the connection is made directly over the casing 156.Optionally, and in a similar manner to that illustrated in FIG. 8( a)for the variation of the first embodiment, mutatis mutandis, astiffening member may be provided for each strap 214, engaged betweenthe enlarged ends 236 of the corresponding strap arms 214 a, 214 b. Thestiffening member may be in the form of a metallic tab, rod or the like,for example, that projects from one of the ends 236 and is received in atight fit within a complementary recess in the other end 236, and issimilarly configured for minimizing or preventing the ends 236 fromdeforming in an outward radial direction when the mounting set issubjected to high stress. Furthermore, and optionally, a load transferpad may be provided, sandwiched between the ends 236 and the casing 156,the surface of the pad facing the casing being preferably in frictional,load-bearing engagement with the casing. Optionally, the strap arms maybe formed integrally with the saddle member. Alternatively the straparms and the saddle member may be made as separate components weldedtogether, for example, made from different titanium alloys.

In the method claims that follow, alphanumeric characters and Romannumerals used to designate claim steps are provided for convenience onlyand do not imply any particular order of performing the steps.

Finally, it should be noted that the word “comprising” as usedthroughout the appended claims is to be interpreted to mean “includingbut not limited to”.

While there has been shown and disclosed example embodiments inaccordance with the invention, it will be appreciated that many changesmay be made therein without departing from the spirit of the invention.

1.-43. (canceled)
 44. A mounting set for use in mounting an externalstores to a mounting station of an aerospace vehicle, comprising amounting bracket arrangement and a strap arrangement, said bracketarrangement configured for selective reversible engagement with respectto the mounting station and for cooperating with said strap arrangement,said strap arrangement being configured for securing the bracketarrangement to the external stores in load bearing abutment therewith toenable transfer of loads between the external stores and said mountingstation via said bracket arrangement, in operation of said mounting set,said strap arrangement comprising at least one strap configured forcircumscribing at least a portion of a perimeter of an external surfaceof the external stores in abutment therewith; wherein the externalstores are non-metallic and the strap arrangement is configured forproviding a strap deformation that matches a stores deformation of theexternal stores, wherein said external stores comprises a casing havingsaid external surface and a rocket motor, and wherein said storesdeformation is at least one of thermally-induced deformation andpressure-induced deformation responsive to operation of said rocketmotor, in which said rocket motor is fired and the casing is pressurizedto a high pressure, wherein responsive thereto the straps deformgenerally following the elastic strain of the casing in order to preventstress concentration on the casing by the straps.
 45. (canceled)
 46. Themounting set according to claim 44, wherein the at least one strap isconfigured for elastically deforming to provide said strap deformationto enable accommodation of a variation of said perimeter within apredetermined range while providing said load bearing abutment with thestores.
 47. The mounting set according to claim 46, wherein the at leastone strap is configured for providing said load bearing abutment withthe external stores for a predetermined range of external loading tosaid external stores via said mounting station, and to further allowsaid elastic deformation while maintaining said load bearing abutmentwith the external stores.
 48. The mounting set according to claim 46,wherein the at least one strap is configured for providing said loadbearing abutment with the external stores for a predetermined range ofthermal loading with respect to said external stores, and to furtherallow said elastic deformation while maintaining said load bearingabutment with the external stores.
 49. The mounting set according toclaim 46, wherein the at least one strap comprises a modulus ofelasticity such as to provide an elastic deformation of at least 0.8%,while providing a datum loading at an elastic deformation of at least0.2%, said datum loading being sufficient to provide said load-bearingabutment at said range of external loads.
 50. The mounting set accordingto claim 46, wherein said external loads may be generated byaccelerations between about 5 g and about 10 g.
 51. The mounting setaccording to claim 44, wherein the at least one strap is made from anyone of: titanium alloys, including Ti-β alloys, Ti-15V-3Cr-3Al-3Sn;composite materials, including carbon fiber composites, Kevlarcomposites; superelastic alloys and/or shape memory alloys includingNitinol, CuZnAl, or CuAlNi alloys.
 52. The mounting set according toclaim 44, said mounting bracket arrangement comprising a mountingbracket configured for said selective reversible engagement with respectto the mounting station and a base portion configured for said loadbearing abutment with the stores.
 53. The mounting set according toclaim 44, wherein the at least one strap is configured for substantialfriction-free abutment with respect to said external surface.
 54. Themounting set according to claim 44, wherein said mounting bracketcomprises an attachment lug configured for releasable engagement with acomplementary hook member comprised at said mounting station.
 55. Themounting set according to claim 52, wherein said base portion is in theform of a saddle member having a contact surface configured for abuttinga part of said external surface, the or each mounting bracket beingjoined to said saddle member.
 56. The mounting set according to claim55, wherein said contact surface is configured for substantialfrictional abutment with respect to said external surface.
 57. Themounting set according to claim 55, said saddle member comprising atleast one saddle flange for allowing overlying abutting connection ofthe at least one strap with respect therewith such as to sandwich eachsaid saddle flange between said external surface and a correspondingoverlying portion of the corresponding strap during operation of saidset.
 58. The mounting set according to claim 57, wherein said overlyingportion of the or each said strap is configured for substantialfriction-free abutment with respect to the or each corresponding saidsaddle flange.
 59. The mounting set according to claim 44, each saidstrap comprising a strip of material having opposite ends, and furthercomprising a suitable connection arrangement configured for connectingsaid ends together such as to enable said strap to circumscribe saidperimeter.
 60. The mounting set according to claim 57, said saddlemember comprising two axially spaced said saddle flanges and having saidat least one bracket disposed therebetween, and further comprising twosaid straps, each said strap being in overlying relationship with arespective one of said saddle flanges.
 61. The mounting set according toclaim 55, said saddle member further comprising a primary thrust padconfigured for cooperating with an ejection piston mechanism that may becomprised at the said mounting station during operation of said ejectionpiston mechanism.
 62. The mounting set according to claim 61, whereinsaid primary thrust pad is in the form of a secondary flange projectingfrom said saddle flange.
 63. The mounting set according to claim 55,said saddle member further comprising a plurality of secondary thrustpads configured for cooperating with a sway brace mechanism that may becomprised at the said mounting station while said stores is mounted tosaid mounting station.
 64. A mounting set for use in mounting anexternal stores to a mounting station of an aerospace vehicle,comprising a mounting bracket arrangement and a strap arrangement, saidbracket arrangement configured for selective reversible engagement withrespect to the mounting station and for cooperating with said straparrangement, said strap arrangement being configured for securing thebracket arrangement to the external stores in load bearing abutmenttherewith to enable transfer of loads between the external stores andsaid mounting station via said bracket arrangement, in operation of saidmounting set, said strap arrangement comprising at least one strapconfigured for circumscribing at least a portion of a perimeter of anexternal surface of the external stores in abutment therewith; whereinthe external stores are non-metallic and the strap arrangement isconfigured for providing a strap deformation that matches a storesdeformation of the external stores, wherein said external storescomprises a casing having said external surface and a pressure vessel,and wherein said stores deformation is at least one of thermally-induceddeformation and pressure-induced deformation responsive topressurization of said pressure vessel to a high pressure, whereinresponsive thereto the straps deform generally following the elasticstrain of the casing in order to prevent stress concentration on thecasing by the straps.
 65. A method for mounting an external stores to amounting station of an aerospace vehicle, comprising: (a) providing atleast one mounting set as defined in claim 44; (b) engaging each saidmounting set with respect to said external surface of the respectiveexternal stores; and (c) engaging each said mounting bracket to arespective said mounting station of said aerospace vehicle.
 66. A methodfor mounting an external stores to a mounting station of an aerospacevehicle, comprising: (a) providing at least one mounting set as definedin claim 64; (b) engaging each said mounting set with respect to saidexternal surface of the respective external stores; and (c) engagingeach said mounting bracket to a respective said mounting station of saidaerospace vehicle.
 67. A mounting set for use in mounting an externalstores comprising a non metallic casing and a rocket motor to a mountingstation of an aerospace vehicle, the mounting set comprising: a mountingbracket arrangement; and a deformable strap arrangement connected to themounting bracket when assembled, the deformable strap arrangementsecuring the bracket arrangement to the non metallic casing of theexternal stores in load bearing abutment with the non metallic casing toenable transfer of loads between the external stores and the mountingstation via the bracket arrangement during operation of the mounting setwhen the rocket motor is fired resulting in thermally-induceddeformation and pressure-induced deformation as the casing ispressurized and expands, the deformable strap arrangement comprising atleast one deformable strap circumscribing at least a portion of aperimeter of an external surface of the external stores in abutmenttherewith when assembled, the deformable strap arrangement beingstructurally tailored in band strength to provide strap deformation thatmatches operational deformation of the non metallic external stores whenfiring the rocket motor due to the non metallic casing expanding andresulting elastic strain of the non metallic casing in order to preventstress concentration on the non metallic casing of the external storesby the straps.